HAN基电控固体推进剂电热耦合特性及燃烧特性实验研究

Experimental Study on Electrothermal Coupling and Combustion Characteristics of HAN-Based Electrically Controlled Solid Propellant

关键词:  电控固体推进剂  电热耦合特性  燃烧性能  电化学分解  热分解反应

Key words:  Electrically controlled solid propellant  Electrothermal coupling characteristics  Combustion performance  Electrochemical decomposition  Thermal decomposition reaction

摘要:

为了探究HAN基电控固体推进剂（ECSP）的电热耦合特性和燃烧性能，通过改变施加电压和环境压力对ECSP进行燃烧性能测试。在ECSP燃烧性能测试装置中采用电压、电流探头记录燃烧过程中通过推进剂的电压和电流，利用高速摄影仪记录推进剂的燃烧过程，借助法拉第电化学分解定律计算推进剂理论电化学分解质量在总燃烧消耗质量中的占比，分析电压和压力对推进剂燃速和质量损失的影响，同时拟合出ECSP燃速（r）与功率（P）和压力（p）的经验公式。结果表明：随着电压和压力的增加，ECSP理论电化学分解质量和实际燃烧质量增加，电解质量占比降低，燃速和质量损失增加。在ECSP的可控燃烧范围内，其燃速与功率和压力满足r = 0.0105P^0.705p^0.251。本文得到了热分解反应在ECSP的燃烧过程中占主导地位是高压力下造成推进剂不可控燃烧的主要原因，为揭示ECSP的燃烧可控机理提供理论基础。

Abstract:

In order to explore the electrothermal coupling characteristics and combustion performance of HAN-based electrically controlled solid propellant （ECSP）， the combustion performance test of ECSP was performed by changing the voltage and pressure. In the ECSP combustion performance test device， voltage probe and current probe were used to record the voltage and current passing through the propellant during the combustion process. The combustion process of propellant was recorded by high speed camera. According to Faraday's law of electrochemical decomposition， the proportion of theoretical electrochemical decomposition mass in total combustion consumption mass of propellant was calculated. The effects of voltage and pressure on the burning rate and mass loss of propellant were analyzed， and the empirical formulas of ECSP burning rate （r） and power （P） and pressure （p） were fitted. The results show that with the increase of voltage and pressure， the theoretical electrochemical decomposition mass and actual combustion mass of ECSP increase， the electrolysis mass ratio decreases， and the burning rate and mass loss increase. Within the controllable combustion range of ECSP， the empirical formula of ECSP burning rate can be fitted as r = 0.0105P^0.705p^0.251. This article shows that the thermal decomposition reaction is dominant in the combustion process of ECSP and is the main reason for the uncontrollable combustion of the propellant under high pressure. It provides a theoretical basis for revealing the controllable combustion mechanism of ECSP.